garmin g1000 integrated avionics system installed in ... · garmin g1000 integrated avionics system...

MOONEYM20M

AFM SUPPLEMENTGARMIN G1000 INTEGRATED AVIONICS SYSTEM

ISSUED 11 - 2004 1 of 36REVISION A 06--2005

FAAAPPROVEDREVISION B 03--2006

MOONEY AIRPLANE COMPANY, INC.LOUIS SCHREINER FIELD KERRVILLE, TEXAS 78028

FAA APPROVEDAIRPLANE FLIGHT MANUAL SUPPLEMENT

FOR

GARMIN G1000INTEGRATED AVIONICS SYSTEM

INSTALLED IN MOONEY M20M

REG. NO. _____________________________________________

SERIAL NO. ____________________________________________

This Supplementmust be attached to theFAAApprovedAirplaneFlightManual when the GARMIN G1000 Integrated Avionics System isinstalled in accordance with Mooney Drawing Number 950300. The in-formation contained herein supplements and / or replaces the informa-tion of the basic Airplane Flight Manual. For Limitations, ProceduresandPerformance information not contained in this Supplement, consultthe basic Airplane Flight Manual.

FAA APPROVED

Michele M. Owsley

Manager, Aircraft Certification OfficeFEDERAL AVIATION ADMINISTRATION2601 Meacham BoulevardFort Worth, Texas 76137-0150

CopyrightE 2006 All Rights Reserved Mooney Airplane Company -- Louis Schreiner Field Kerrville, Texas 78028SUPP0002B

MOONEYM20M


2 of 36 ISSUED 11 - 2004REVISION A 06--2005

FAAAPPROVED REVISION B 03--2006

LOG OF REVISIONS

REV.NUMBER

PAGENUMBER(S)

DESCRIPTION FAAAPPROVED

APR’VDDATE

A 7, 19, 31,32

16 thru 21

23, 25, 29

Add following componentsfrom Garmin G1000 Cockpit

Reference Guide:GDL 69ADMEADF

Added ModificationsRelated to Optional A/C

Added Plural Reference toAlternator

B 19, 20, 32 Add SKYWATCHtCapability

THE REVISED PORTIONS OF AFFECTED PAGES ARE INDICATED BY VERTICALLINES IN THE MARGIN.

MOONEYM20M




TABLE OF CONTENTS

SECTION PAGE

I GENERAL 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

II LIMITATIONS 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

III EMERGENCY PROCEDURES 15. . . . . . . . . . . . . . . . . . . . . . . . .

IV NORMAL PROCEDURES 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

V PERFORMANCE 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

VI WEIGHT AND BALANCE 29. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

VII AIRPLANE AND SYSTEM DESCRIPTIONS 29. . . . . . . . . . . . . .

VIII SERVICING AND HANDLING 36. . . . . . . . . . . . . . . . . . . . . . . . . .

IX SUPPLEMENTAL DATA 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

X SAFETY TIPS 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MOONEYM20M




INTENTIONALLY LEFT BLANK

MOONEYM20M




SECTION I -- GENERAL

1. TheGARMING1000 IntegratedAvionicsSystem isa fully integratedflight, engine, communication, navigation and surveillance instru-mentation system. The system consists of a Primary Flight Display(PFD), Multi--Function Display (MFD), audio panel (GMA), Air DataComputer (ADC), Attitude andHeadingReferenceSystem (AHRS),engine / airframe processing unit (GEA), and integrated avionics(GIA) containing VHF communications, VHS navigation, and GPSnavigation.

2. The primary function of the PFD is to provide attitude, heading, airdata, navigation, and alerting information to the pilot. The PFDmayalso beused for flight planning. Theprimary function of theMFD is toprovide engine information, mapping terrain information and forflight planning. The audio panel is used for selection of radios fortransmitting and listening, intercom functions, and marker beaconfunctions.

3. The primary function of the VHF Communication portion of theG1000 is to enable external radio communication. Theprimary func-tion of the VOR/ILS Receiver portion of the equipment is to receiveanddemodulateVOR, localizer, andGlideSlopesignals. Theprima-ry functionof theGPSportionof the system is toacquire signals fromthe GPS satellites, recover orbital data, make range and Dopplermeasurements, and process this information in real time to obtainthe user’s position, velocity, and time.

4. Provided the GARMIN G1000 GPS receivers are receiving ade-quate and usable GPS and/or VHF navigation signals, it has beendemonstrated capable of andmeets the accuracy specifications forthe following types of flight operations:

VFR/IFR en--route, oceanic, and terminal operations aswell as non-precision instrument approach (GPS, Loran--C, VOR, VOR--DME,TACAN,NDB,NDB--DME,RNAV) operationwithin theU.S.NationalAirspace System in accordance with AC20--138A.

Navigation in the North Atlantic Minimum Navigation PerformanceSpecification (MNPS)Airspace inaccordancewithAC91--49andAC120--33.

The GARMIN G1000 system meets RNP5 airspace (BRNAV) re-quirements of AC 90--96 and in accordance with AC 20--138A, JAAAMJ 20X2 Leaflet 2 Revision 1, and FAA Order 8110.60 for oceanicand remote

MOONEYM20M




airspace operations, provided it is receiving usable navigation infor-mation from the GPS receiver. (A separate software application forprediction ofGPSnavigation availabilitymay be required for oceanicand remote operations. Refer to appropriate limitations for the air-space you are operating in to determine if this GPS prediction soft-ware is required.)

Navigation is accomplished using the WGS--84 (NAD--83) coordinatereference datum. GPS navigation data is based upon use of only theGlobal Positioning System (GPS) operated by the United States ofAmerica.

MOONEYM20M




SECTION II -- LIMITATIONS

GENERAL

G1000 System:

1. TheGARMING1000Cockpit ReferenceGuide for theM20MSeriesaircraft, P/N 190--00450--01, Revision A or later approved revisionmust be immediately available to the flight crew.

2. TheGARMING1000mustutilize the followingor later FAAapprovedsoftware versions:

SUB--SYSTEM SOFTWARE VERSION

PFD 4.06

MFD 4.06

GMA 2.08

AHRS 2.03

ADC 2.05

GIA 2.08

GEA 2.04

GPS 3.01

The database version is displayed on theMFDpower--up page immedi-ately after system power--up and must be acknowledged. The remain-ing system software versions can be verified on the AUX group sub--page 5, “AUX – SYSTEM STATUS”.

3. IFR enroute, oceanic and terminal navigation predicated upon theG1000 GPS Receiver is prohibited unless the pilot verifies the cur-rency of the database or verifies each selected waypoint for accura-cy by reference to current approved data.

MOONEYM20M




4. Instrument approach navigation predicated upon the G1000 GPSReceiver must be accomplished in accordance with approved in-strument approach procedures that are retrieved from the GPSequipment database. The GPS equipment database must incorpo-rate the current update cycle.

(a) Instrument approaches utilizing the GPS receiver must beconducted in the approach mode and Receiver AutonomousIntegrity Monitoring (RAIM)must be available at the Final Ap-proach Fix.

(b) Accomplishment of ILS, LOC, LOC--BC, LDA, SDF, MLS oranyother typeof approachnot approved forGPSoverlaywiththe G1000 GPS receiver is not authorized.

(c) Use of the G1000 VOR/ILS receiver to fly approaches not ap-proved for GPS require VOR/ILS navigation data to be validon the PFD display.

(d)When an alternate airport is required by the applicable operat-ing rules, it must be served by an approach based on otherthan GPS navigation, the aircraft must have the operationalequipment capable of using that navigation aid, and the re-quired navigation aid must be operational.

(e) VNAV information may be utilized for advisory informationonly. Use of VNAV information for Instrument Approach Pro-cedures does not guarantee step--down fix altitude protec-tion, or arrival at approach minimums in a normal position toland. VNAV also does not guarantee compliance with inter-mediate altitude constraints between the top of descent andthe waypoint where the VNAV path terminates in terminal orenroute operations.

5. If not previously defined, the followingdefault settingsmust bemadein the “SYSTEMSETUP”menuof theG1000prior to operation (referto Pilot’s Guide for procedure, if necessary.

(a) DIS, SPD…..nmkt (sets navigation units to “nautical miles”

and “knots”)

(b) ALT, VS……..ft fpm (sets altitude units to “feet” and “feet perminute”)

MOONEYM20M




(c) MAP DATUM….WGS 84 (sets map datum to WGS--84, [seenote below])

(d) POSITION……..deg--min (sets navigation grid units to deci-mal minutes)example: dd.mm.ss: 45_ 30’ 30” in decimal minutes are: 45_30.5’

NOTE:In some areas outside the United States, datums other thanWGS--84 or NAD--83 may be used. If the G1000 is authorizedfor use by the appropriate Airworthiness authority, the re-quired geodetic datum must be set in the G1000 prior to itsuse for navigation.

6. Operation is prohibited north of 70oNand south of 70oS latitudes. Inaddition, operation is prohibited in the following two regions: 1) northof 65oNbetween75oWand120oW longitudeand 2) south of 55oSbetween 120o E and 165o E longitude.

7. CAUTION: CDI automatic source switching to the ILSonNav 1 or 2must beset tomanual for instrumentapproachesconductedwith theautopilot coupled. If the CDI navigation source is changed when au-topilot is engaged in GPSS mode, the S--Tec 55x autopilot lateralmode will revert to wings level mode and indicate GPSS FAIL. NAVmode must be manually reselected by the pilot in order to track theILS or Localizer.

8. Display of autopilot operationalmode on thePFD is supplemental tothedatawhich is presentedon thedisplayof theS--Tec55Xautopilotcontrol unit.

2.1 AIRSPEED MARKINGS – M20M

Marking IAS Significance

Red band 20 KIAS – 59 KIAS Low speed awareness -- stall isimminent

White band 59 KIAS – 110 KIAS Operating range with flaps fully ex-tended

Green band 66 KIAS – 174 KIAS Normal operating range

Yellow band 174 KIAS -- 195 KIAS Caution range -- smooth air only

Red band 195 KIAS and greater Lower limit of 195 KIAS is the maxi-mum speed for all operations

The airspeed indicator is marked in IAS values.

MOONEYM20M




2.2 POWER PLANT INSTRUMENT MARKINGS

Power plant instrument markings and their color code significance areshown in the table below.

NOTE:

When an indication lies in the caution range, the legend forthat display will change to the color of the caution range.When an indication lies in the upper or lower prohibitedrange, the legend for that display will change to the color ofthe prohibited range and will begin flashing as well.

MOONEY M20M

Indication Redarc / bar

=Lower

prohibitedrange

Yellowarc / bar

=Cautionrange

Greenarc / bar

=Normaloperatingrange

Yellowarc / bar

=Cautionrange

Redarc / bar

=Upper

prohibitedrange

Engine RPM ---- ---- 2200 - 2500 ---- 2500 - 2650*

ManifoldPress. In. Hg

---- ---- 10 - 38 ---- -- > 38

Oil Temp oF ---- ---- 100 - 245 ---- >245

Cyl. Head

Temp oF---- ---- 250 - 500 ---- >500

Oil Press PSI 0 - 25 25 - 55 55 - 95 95 - 115 >115

Fuel Press -PSI

0 - 15 15 - 24 25 - 55 - - > 55

Turbine InletTemperature

---- ---- 0 - 1750 ---- > 1750

* To prevent nuisance alerts during normal takeoffs: the “RPM”will notturn red or flash until the RPM exceeds 2640.

MOONEYM20M




2.3 -- TYPES OF OPERATION

The airplane is approved for the following operations when equipped inaccordance with FAR 91 or FAR 135.

(a) Day V.F.R.

(b) Night V.F.R

(c) Day I.F.R.

(d) Night I.F.R.

(e) Non Icing

Minimum Operational Equipment for flight operations listed:

Equipment Numberinstalled

VFRDay

VFRNight

IFR

Primary Flight Display 1 * 1 1

Multi--Function Display 1 -- 1 1

Audio panel 1 -- -- 1

Air data computer 1 1 1 1

Attitude and Heading Reference System 1 -- 1 1

GPS 2 -- 1 2

* If the PFD is inoperative or removed for service, the MFD may beusedas thePFD.TheMFDdisplaymust beoperated inPFD (reversion-ary) mode by depressing the reversionary button on the Audio Panel.When operating in reversionarymode the system is limited to DAYVFRoperations only.

2.4 -- ADVISORY MESSAGES

TheG1000Cockpit ReferenceGuide and theG1000Pilot’s Guide con-tain detailed descriptions of the annunciator system and all advisorymessages. Thesemessages appear on the PFD for flight crew aware-ness.

The following warnings and cautions may appear in various locationson the PFD or MFD. Consult the G1000 Cockpit Reference Guide andthe G1000 Pilot’s Guide for detailed descriptions of each annunciationas necessary.

MOONEYM20M




Annunciation Cause

AHRS Aligning – KeepWings Level

AttitudeandHeadingReferenceSystem isaligning. Keep wings level using standbyattitude indicator.

ATTITUDE FAIL Display system is not receiving attitudereference information from the AHRS; ac-companied by the removal of sky/groundpresentation and a red X over the attitudearea.

AIRSPEED FAIL Display system is not receiving airspeedinput from the air data computer; accom-paniedbya redX through theairspeeddis-play

ALTITUDE FAIL Display system is not receiving airspeedinput from the air data computer; accom-paniedbya redX through thealtimeter dis-play

VERT SPEED FAIL Display system is not receiving verticalspeed input from the air data computer;accompanied by a red X through the verti-cal speed display

HDG Display system is not receiving valid head-ing input from the AHRS; accompanied bya red X through the digital heading display

Red X A red X through any display field, such ascom frequencies, nav frequencies, or en-gine data, indicates that display field is notreceiving valid data.

MOONEYM20M




DECALS AND PLACARDS

M20M GX FLIGHT PANEL PLACARD LOCATIONS

1 150056-1001 SPEEDBRAKE EQUIPPED FOR OPERATING...

2 150056-1004 N NUMBER

3 150056-1012 14V RECEPTACLE

4 800399-007 PANEL LIGHTS/GLARESHIELD

5 150056-1010 MIXTURE PUSH RICH

6 150056-1007 PROP PUSH INCREASE

7 150056-1008 THROTTLE PUSH INCREASE

8 150056-3017 LIGHTING DETECTION EQUIP. OPT...

9 150056-1009 PULL FOR ALTERNATE STATIC SOURCE

10 150056-3038 [STD] GEAR UP/DOWN /BYPASS

10 150085-038 [OPT] GEAR UP/DOWN /BYPASS

11 150056-3039 MIC <CWS A/P DISC TRIM INTR>

REFLOCATION

PARTNUMBER

DECAL/PLACARDNOMENCLATURE

1

2

3456789 10

11

MSUP - 01

NOTE:

150056--1003 Decal is required only when the McCauley 2Blade Propeller is installed.

MOONEYM20M




INTENTIONALLY LEFT BLANK

MOONEYM20M




SECTION III -- EMERGENCY PROCEDURESGENERAL

1. These checklists supercede those in the POH as a result of theinstallation of the G1000 avionics system. All other emergency pro-cedures in the POH remain in effect.

2. These checklists assume that the aircraft is equippedwith a standbyalternator system installed by Mooney Airplane Company, Inc.

3. If GARMING1000GPSnavigation information is not available or in-valid, utilize remaining operational navigation equipment as re-quired.

4. If the ”POSNERROR” annunciation is displayed the systemwill flagand no longer provide GPS based navigational guidance. The crewshould revert to the G1000 VOR/ILS receivers or an alternatemeans of navigation other than the G1000 GPS receivers.

5. If the ”POSN ERROR” annunciation is displayed in the enroute,oceanic, terminal, or initial approach phase of flight, continue to nav-igate using the GPS equipment or revert to an alternate means ofnavigation other than the G1000 GPS receiver appropriate to theroute and phase of flight. When continuing to use GPS navigation,position must be verified every 15 minutes using the G1000 VOR/ILS receiver or another IFR--approved primary navigation system.

6. CAUTION: If the ”POSN ERROR” annunciation is displayed whileon the final approach segment (between the Final Approach Fix andtheMissedApproach Point), GPSbased navigationwill continue forup to 5minuteswith approachCDI sensitivity set at 0.3 nauticalmile.It is recommended that the pilot initiate the missed approach uponreceipt of this message from the G1000. Navigation guidance willcontinue for 5 minutes allowing the pilot to initiate the missed ap-proach while maintaining course guidance on the final approachcourse. Then the systemwill flag and no longer provide course guid-ance with approach sensitivity. Missed approach course guidancemaystill beavailablewith1nauticalmileCDI sensitivity byexecutingthe missed approach. This is typically caused by the GPS sensor’sinability to provide adequate horizontal position accuracy for the fi-nal approach segment. It is possible, however unlikely, that theGPSpositionmay degrade to the point where terminal operations cannotbe supported for the missed approach segment. Navigate usingother primary navigation equipment (VOR receivers, etc) if this oc-curs.

MOONEYM20M




7. In an in--flight emergency, depressing and holding the “Comm”transfer button for 2 seconds will select the emergency frequency of121.500 MHz, and will show it in the ”Active” frequency window.

8. The Attitude, Heading and Reference System (AHRS) requires atleast one GPS or air data input to function properly. In the unlikelyevent that both GPS position sources fail, and the air data computerfails, the AHRS will subsequently lose attitude and heading and thepilot will be required to use the standby instrumentation. In thisinstance, thePFDwill not provide altitude, airspeed, attitude, or nav-igation information

3.1 -- EMERGENCY PROCEDURE CHECKLISTS

Use the electrical fire checklists found in the M20M POH and appropri-ate AFM supplements.

ELECTRICAL FIRE - IN FLIGHT (M20M W/O OPTIONAL AIR CON-DITIONING)

If electrical power is essential for the flight, attempt to isolate the faultycircuit.

Cabin Ventilation OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Heating Controls CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Circuit Breakers CHECK to identify fault circuit if possible. . . . . . . . . .

Land as soon as practical.

If smoke in thecockpit continues, press theEMERGBUSswitch to shedthe non--essential equipment.

NOTE:

If the autopilot is engaged and theEMERGBUS is activated, itwill disengage without annunciation.

If smoke in the cockpit continues, then:

Left and Right Alternator Switches OFF. . . . . . . . . . . . . . . . . . . . . . . . .

Master Switch OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NOTE:

The standby instrumentation will remain powered with theEMER BUS switch ON.

MOONEYM20M




If power must be re-established to navigation equipment to continueflight: If the faulty component canbedetermined, pull the associated cir-cuit breaker if not tripped already. Do not close the open breaker to re--establish power to the failed circuit.If the faulty component cannot be determined, pull all essential circuitbreakers, switch the Master switch ON and L & R Alternator switchesON; then close circuit breakers one at a time. Permit a short time toelapse before closing the next circuit breaker.

ELECTRICAL FIRE - IN FLIGHT (M20M WITH OPTIONAL AIR CON-DITIONING)

If electrical power is essential for the flight, attempt to isolate the faultycircuit.

Cabin Ventilation OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Heating Controls CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Circuit Breakers CHECK to identify fault circuit if possible. . . . . . . . . .Land as soon as practical.If smoke in the cockpit continues, press the EMERG BUS switch andpull theBATT circuit breaker to shed the non--essential equipment andenergize the Standby 20 amp alternator.

NOTE:

If the autopilot is engaged and the EMERG BUS is activatedand the BATT circuit breaker, it will disengage without an-nunciation.

If smoke in the cockpit continues, then:

Alternator Switch OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Master Switch OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NOTE:

The standby instrumentation will remain powered with theEMER BUS switch ON.

If powermust be re-established to the navigation equipment to continueflight: If the faulty component canbedetermined, pull the associated cir-cuit breaker if not tripped already. Do not close the open breaker to re--establish power to the failed circuit.If the faulty component cannot be determined, pull all essential circuitbreakers, switch the Master switch ON and Alternator switch ON; thenclose circuit breakers one at a time. Permit a short time to elapse beforeclosing the next circuit breaker.

MOONEYM20M




ELECTRICAL SYSTEM FAILURES (M20M W/O OPTIONAL AIR CON-DITIONING)

1. All electrical systems will remain powered and functional.

2. Reduce the electrical load if the ammeter indicates a battery dis-charge.

3. Turn off the affected alternator field switch. Land as soon as practi-cal.

NOTE:

It is permissible to cycle the alternator field switch to attemptto reset the alternator.

4. If both alternators fail and cannot be restored, then:

5. Reduce the loadbypressing theEMERBUSswitch.This loadshedsthe non--essential bus. The following systems remain powered bythe essential bus:

Left / Right Alternator FailureS L/R ALT SENSES L/R ALT FIELDS LEFT ALTS AUX PANELS BATS AUX OVHDS RIGHT ALTS BOOST PUMPS GLRSHIELD LIGHTS PFDS MFDS AHRSS ADCS ENGINE INSTS STBY GYROS ICE PROT SYS (if installed)S COM 1S NAV 1 / GPS 1S AUDIOS XPONDRS ICE LITES PITOT HEAT

MOONEYM20M




The following systems on the non--essential bus will be unpowered:

S TURN COORDINATOR (AUTOPILOT INOP)S COM 2S NAV 2 / GPS 2S WX STORMSCOPES DIMMER CONTROLS ADF/DME/DATA LINKS TRAFFIC ALERT

CAUTION:If the autopilot is engaged, when the EMER BUS switch is acti-vated the autopilot will disconnect without annunciation.6. Terminate flight as soon as practicable.

7. If using battery power only and the primary battery has been de-pleted (minimum of 18 VDC), the pilot may select the alternate bat-tery using themain battery selection switch. Therewill be no changein available equipment when changing battery sources. All equip-ment powered previously will remain powered.

ELECTRICAL SYSTEM FAILURES (M20M WITH OPTIONAL AIRCONDITIONING)

If the Main Alternator fails, indicated by the Master Warning “ALTVOLTS” is flashing:

Perform theStandbyAlternator EmergencyChecklist (repeated below)

8. Push the “Stby Alt/Emergency Bus” switch ON. (This activates theemergency bus circuitry & Standby Alternator system) Verify:

-- A) The AMBER “EMERG BUS” annunciator illuminates, and-- B) The RED “ALT VOLTS” flashing annunciator extinguishes.

NOTE:

The most efficient operating RPM is 2575 RPM when operat-ing on the Standby Alternator System.

9. All electrical systems will remain powered and functional.

10.If the RED “ALT VOLTS” annunciator remains illuminated, then:

CAUTION:If the RED “ALT VOLTS”annunciation remains illuminated, thenthe standby alternator has failed, and only main battery power re-mains.

11.Reduce the electrical load by pulling the “BATT” circuit breaker. Thisload sheds the non--essential bus. The following systems remainpowered by the essential bus.

MOONEYM20M




CAUTION:If the autopilot is engaged, when the BATT circuit breaker ispulled, the autopilot will disconnect without annunciation.S ALT SENSES EMER ALT BUSS ALT FIELDS EMER ALT FIELDS ALT OUTS STBY ALTS BATTS AUX PANELS AUX OVHDS GLRSHIELD LIGHTS PFDS MFDS AHRSS ADCS ENGINE INSTS STBY GYROS ICE PROT SYSS COM 1S NAV1 / GPS1S AUDIOS XPONDRS STALL WARNS ICE LITES PITOT HEAT

The following systems on the non-essential bus will be unpoweredS COM 2S NAV2 / GPS2S ALL LIGHTING ON THE OVERHEAD PANELS FUEL PUMPSS AUTOPILOTS ELECTRIC TRIMS LANDING GEAR MOTOR AND INDICATORS COWL FLAPSS DEFROST BLOWERS WX STORMSCOPES SKYWATCHt

MOONEYM20M




12.Terminate flight as soon as practical

13.On approach, the pilot may engage the “BATT” circuit breaker to re--establish power to all systems is necessary.

14.If using battery power only and the primary battery has been de-pleted (minimum of 18 VDC), the pilot may select the alternate bat-tery using themain battery selection switch. Therewill be no changein available equipment when changing battery sources. All equip-ment powered previously will remain powered.

AVIONICS EMERGENCIES

a) PFD OR MFD DISPLAY FAILURE

1. DISPLAY BACKUP button on audio panel PUSH. . . . . . . . . . . .

b) AHRS FAILURE

NOTE:

failure of the Attitude andHeadingReference System (AHRS)is indicated by a removal of the sky/ground presentation anda redXandayellow“AHRSFAILURE”shownon thePFD. Thedigital heading presentation will be replaced with a yellow“HDG” and the compass rose digits will be removed. Thecourse pointerwill indicate straight up and coursemaybe setusing the digital window.

1. Use Standby Attitude Indicator and Magnetic compass.

2. Course Set using digital window. . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. Land as soon as practical.

c) AIR DATA COMPUTER (ADC) FAILURE

NOTE:

Complete lossof theAirDataComputer is indicatedbya redXand yellow text over the airspeed, altimeter, vertical speed,TASandOATdisplays. SomeFMS functions, suchas true air-speed and wind calculations, will also be lost.

1. Use Standby Airspeed Indicator and Altimeter

2. Land as soon as practical at a suitable airport

d) ERRONEOUSORLOSSOFENGINEANDFUELDISPLAYS

MOONEYM20M




NOTE:

Loss of an engine parameter is indicated by a red X throughthe data field. Erroneous informationmay be identified by in-dications which do not agree with other system information.Erroneous indications may be determined by comparing adisplay with other displays and other system information.

1. Set power based on throttle lever position, engine noise and speed.

2. Monitor other indications to determine the health of the engine.

3. Use known power settings in the POH Chapter V for approximatefuel flow values.

4. Use other system information, such as annunciator messages, fuelquantity and flow, to safely complete the flight.

e) ERRONEOUS OR LOSS OF WARNING/CAUTIONANNUNCIATORS

NOTE:

Loss of an annunciator may be indicated when engine or fueldisplays show an abnormal or emergency situation and theannunciator is not present. An erroneous annunciator maybe identified when an annunciator appears which does notagree with other displays or system information.

1. If an annunciator appears, treat it as if the condition exists. Refer tothe POH/AFM Emergency or Abnormal procedures or the proce-dures contained in this AFMS.

2. If a display indicates an abnormal condition but no annunciator ispresent, use other system information, such as engine displays, fuelquantity and flow, to determine if the condition exists. If it cannot bedetermined that the condition does not exist, treat the situation as ifthe condition exists.Refer to thePOH/AFMEmergency orAbnormalprocedures or the procedures contained in this AFM Supplement.

MOONEYM20M




SECTION IV -- NORMAL PROCEDURES

NOTE:

View ability of the PFD and MFD displays may be degradedwhen wearing polarized sunglasses.

The following normal procedures have been modified as the result ofthe G1000 installation. Procedures which have not beenmodified as aresult of the G1000 installation should be used as written in the POH/AFM.

DETAILED OPERATING PROCEDURES

Normal operating procedures for the G1000 are described in the GAR-MIN G1000 Cockpit Reference Guide and the GARMIN G1000 Pilot’sGuide.

4.5 -- NORMAL PROCEDURES CHECKLISTS

BEFORE STARTING ENGINE

Preflight Inspection Complete. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Seats, Seatbelt, Shoulder Harness Adjust and Secured. . . . . . . . . . . .

Magneto/Starter Switch Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Master Switch On. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Alternator Field Switch(es) Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fuel Boost Pump Switches Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Circuit Breaker Switches Check--All In. . . . . . . . . . . . . . . . . . . . . . . . . .

ELT Switch Armed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Rocker Switches Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Alternate Static Source Push Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Throttle Closed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Propeller Full Forward (High RPM). . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Mixture Idle Cut Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cowl Flaps Verify Full Open. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Brakes Set. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Wing Flap Switch Flaps Up. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MOONEYM20M




Defrost Push Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cabin Heat Push Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cabin Vent As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fuel Selector Fullest Tank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Landing Gear Switch Down Position. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Red Emergency Gear Extension Handle Down and Latched. . . . . . . .

Internal Lights Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Passenger Briefing Completed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Refer to SECTION IX -- Supplemental Data for other Optional Equip-ment Procedures and Checks.

BEFORE TAXI

Engine Start Checklist Completed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Elevator Trim Switch On. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Internal/External Lights As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PFD/MFD Check Normal Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Comm/Nav Radios Checked and Set. . . . . . . . . . . . . . . . . . . . . . . . . . .

Altimeter Set. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fuel Selector Switch Tanks, verify engine runs on other tank. . . . . . .

Cowl Flaps Full Open or As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cabin Heat As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Defroster As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cabin Vent As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Flight Plan As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Optional Equipment Checks Reference Section IX. . . . . . . . . . . . . . .

NOTE:

During cold weather, ground operations may be conductedwith cowl flaps positioned partially or fully closed to helpkeep engine temperatures in normal operational ranges priorto takeoff. However, if cowl flaps are fully closed, monitor en-gine temperatures to avoid exceeding maximum allowablelimits.

MOONEYM20M




TAXI

Before Taxi Checklist Completed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Rudder Trim As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

-CAUTION-With Rudder Trim in the full right position the aircraft will tend tosteer to the right during taxi.

Parking Brake Release. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Brakes Check during taxi. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Heading Indicator Proper Indication During Turns. . . . . . . . . . . . . . . .

PFD/MFD No Flags/Red X’s. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Throttle Minimum Power. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Propeller Full Forward (High RPM). . . . . . . . . . . . . . . . . . . . . . . . . . . . .

-CAUTION-To prevent battery depletion in prolonged taxi or holding positionbefore takeoff, increase RPM until the “AMPS” indication on theG1000 indicates a positive number.

BEFORE TAKEOFF

Taxi Checklist Complete. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Parking Brake Set. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fuel Selector Fullest Tank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Throttle 1000 RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cowl Flaps Open or As Desired. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Propeller High RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Mixture Full Forward. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Alternate Air Verify Closed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Alternator Field Switch(es) Verify ON. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Throttle 2000 RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


Magneto Switch Check – BOTH to L, BOTH to R, BOTH. . . . . . . . . . .

MOONEYM20M




Verify engine operates smoothly on each magneto separately(150 RPM MAX drop on each magneto, 50 RPM MAX difference)

NOTE:

An absence of RPM drop may be an indication of faulty mag-neto grounding or improper timing. If there is doubt concern-ing ignitionsystemoperation,RPMchecksat a leanermixturesetting or higher engine speedwill usually confirmwhether adeficiency exists.

Propeller Cycle/Return to High RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Ammeter CHECK Positive Charge Indication. . . . . . . . . . . . . . . . . . . . .

Main Battery Voltage Greater than 26.5VDC. . . . . . . . . . . . . . . . . . . . .

Select the other battery using the BAT 1/2 selector

Ammeter CHECK Positive Charge Indication. . . . . . . . . . . . . . . . . . . . .

Main Battery Voltage Greater than 26.5VDC. . . . . . . . . . . . . . . . . . . . .

Select desired Main Battery for use during flight using BAT 1/2selector

Throttle RETARD to 1000 RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fuel BoostPump Switch ON--Verify annunciator light illuminates BLUE. . . . . . .

Fuel Boost Pump Switch OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Elevator Trim TAKEOFF SETTING. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Rudder Trim TAKEOFF SETTING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Wing Flaps CHECK operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SET AT TAKEOFF POSITION (10 degrees)

Flight Controls CHECK free and correct movement. . . . . . . . . . . . . . .

Cabin Door CHECK SECURED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Seats, Seat Belts and Shoulder Harness SECURED. . . . . . . . . . . . .

Avionics and Autopilot CHECK – (Refer to section IX). . . . . . . . . . . .

Annunciator Lights CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Internal/External Lights AS DESIRED. . . . . . . . . . . . . . . . . . . . . . . . . . .

Strobe Lights/Rotating Beacon ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MOONEYM20M




Pilots Window CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Emergency Gear Extension (RED) Handle DOWN and LATCHED. .

Oil Temperature 100_F(38_C) minimum. . . . . . . . . . . . . . . . . . . . . . . . .

CHT 250_F(121_C) minimum. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Parking Brake RELEASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TAKEOFF

Proper engineoperation should be checkedearly in the takeoff roll. Anysignificant indication of rough or sluggish engine response is reason todiscontinue takeoff. When takeoff must bemade over a gravel surface,it is important that the throttle be applied SLOWLY. This will allow theaircraft to start rollingbeforehighRPM isdeveloped, andgravel or loosematerial will be blown back from the propeller area instead of beingpulled into it.

If the turbocharger and its controlling system are properly rigged, man-ifold pressure will increase to approximately 34 to 38 in. Hg, when thethrottle is full open. However, engine operation with oil temperature be-low 100F (38C)will result in an overboost (manifold pressure above 38in. Hg). If an overboost occurs, retard throttle to lower manifold pres-sure below 38 in. Hg, and continue flight. As the oil warms above 100 F(38 C) the throttle can be moved to full throttle open and the turbochar-ger controller will maintain proper manifold pressure for maximum con-tinuous power.

Full throttle operations during hot weather conditions may also result inmanifold pressure over 38 in. Hg. If this occurs, retard throttle below 38in. Hg, and continue flight.

TAKEOFF (NORMAL)

Power FULL THROTTLE (2575 RPM). . . . . . . . . . . . . . . . . . . . . . . . . .

DO NOT EXCEED 38” MAP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Annunciator CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Blue Boost Pump Light ONEngine Instruments CHECK for proper indications. . . . . . . . . . . . . . . .

Lift Off/Climb Speed As specified in SECTION V (Takeoff Distance).

Landing Gear RETRACT IN CLIMB after clearing obstacles. . . . . . . .

Wing Flaps UP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fuel Pressure 24 PSI (minimum). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MOONEYM20M




NOTE:Ifmaximumperformance takeoffs are desiredobtain full pow-er before brake release. Use lift off and climb speed as speci-fied in Section V.

CLIMB

NOTE:If applicable, use noise abatement procedures as required.See Section V, for rate of climb graph.

CLIMB (CRUISE)

Power 2400 RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Manifold Pressure 34 Inches. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Mixture RICH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


Rudder Trim AS DESIRED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Airspeed 120 KIAS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CLIMB (BEST RATE)(Vy)

Power FULL THROTTLE / 2575 RPM. . . . . . . . . . . . . . . . . . . . . . . . . .Do Not Exceed 38” Map

Mixture RICH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



Airspeed 105 KIAS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CLIMB (BEST ANGLE)(Vx)

Power FULL THROTTLE / 2500 RPM. . . . . . . . . . . . . . . . . . . . . . . . . .

Mixture RICH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



Airspeed 85 KIAS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SHUTDOWN

CAUTIONOperate the engine at idle (below 1000RPM) for 5minutes to allowthe turbocharger to cool. Taxi time after landing may be consid-ered as part of the 5 minutes.

MOONEYM20M





Throttle Idle RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Interior/Exterior Lights Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Pitot Heat Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Magneto/Starter Switch Grounding Check. . . . . . . . . . . . . . . . . . . . . . .

Mixture Idle Cut--Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Alternator Field Switch(es) Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Master Switch Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Magneto/Starter Switch Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SECURING AIRCRAFT

Magneto/Starter Switch Verify Off/Key Removed. . . . . . . . . . . . . . . . .

Master Switch Verify Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Electrical Switches Verify Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Interior Light Switches Verify Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Emergency Bus Switch Verify Off. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Parking Brake Release – Install Wheel Chocks. . . . . . . . . . . . . . . . . . .

Extended Parking Control Wheel Secured. . . . . . . . . . . . . . . . . . . . . . .

Cabin Windows and Doors Closed and Locked. . . . . . . . . . . . . . . . . .Tie aircraft down at wing and tail points.

SECTION V -- PERFORMANCENo change.

SECTION VI -- WEIGHT AND BALANCESee current weight and balance data.

SECTION VII -- SYSTEM DESCRIPTIONS

TheGARMING1000 Integrated Avionics System consists of a PrimaryFlight Display (PFD), a Multi--Function Display (MFD), an Audio Panel,andAttitudeandHeadingReferenceSystem (AHRS), anAirDataCom-puter (ADC), and the sensors and computers to process flight and en-gine information for display to the pilot. The system contains dual GPSreceivers, dual VOR/ILS receivers, dual VHF communications trans-ceivers, a transponder, and an integrated annunciation system to alertthe pilot of certain abnormal conditions.

MOONEYM20M




The Primary Flight Display (PFD) typically displays airspeed, attitude,altitude, and heading information in a traditional format. Slip informa-tion is shown as a trapezoid under the bank pointer. One width of thetrapezoid is equal to a one ball width slip. Rate of turn information isshown on the scale above the compass rose; full scale deflection isequal to a standard rate turn. The following controls are available on thePFD (clockwise from top right):S Communications frequency volume and squelch knobS Communications frequency set knobsS Communications frequency transfer buttonS Altimeter setting knob (baro/QNH set)S Course knobS Map range knob and cursor controlS FMS control buttons and knobS PFD softkey buttons, including master warning/caution acknowl-

edgementS Altitude reference set knobS Heading bug controlS Navigation frequency transfer buttonS Navigation frequency set knobsS Navigation frequency volume and Identifier knob

The PFD displays the crew alerting (annunciator) system. When analert message is received, an aural tone will be heard. Selecting theAlert button will allow the flight crew to see additional information re-garding the alert message.

Trend vectors are shown on the airspeed and altimeter displays as amagenta linepredicting6 secondsat the current rate. The turn rate indi-cator also functions as a trend indicator on the compass scale.

The PFD can be displayed in a composite format for emergency use bypressing the DISPLAYBACKUPbutton on the audio panel. In the com-posite mode, the crew alerting function remains operative, but no mapfunctions are available.

The Multi--Function Display (MFD) typically displays engine data,maps, terrain, traffic and topography displays, and flight planning andprogress information. The display unit is identical to the PFD and con-tains the same controls as previously listed.

The audio panel contains traditional transmitter and receiver selectors,aswell as an integral intercomandmarker beacon system. Themarker

MOONEYM20M




beacon lights appear on the PFD. In addition, a clearance recorder re-cords the last 2 ½ minutes of received audio. Lights above the selec-tions indicate what selections are active. Pressing the red DISPLAYBACKUP button on the audio panel causes both the PFD and MFD todisplay a composite mode.

The Attitude and Heading Reference System (AHRS) uses GPS, ratesensors, air data, andmagnetic variation to determine pitch and roll atti-tude, sideslip and heading. Operation is possible in a degradedmode ifthe system loses any of these inputs, but the AHRSmust have at leasttheADCorGPS input to function. Statusmessagesalert the crewof theloss of any of these inputs. The AHRS will align while the aircraft is inmotion, but will align quicker if the wings are kept level during the align-ment process.

The Air Data Computer (ADC) provides airspeed, altitude, verticalspeed, and air temperature to the display system. In addition to the pri-mary displays, this information is used by the FMS and TIS systems.

Engine instruments are displayed on theMFD. Discrete engine sensorinformation is processed by the GARMIN Engine Airframe (GEA) sub--system. When an engine sensor indicates a value outside the normaloperating range, the legend will turn yellow for caution range, and turnred and flash for warning range.

The G1000 also interfaces to the STEC 55x autopilot and repeats theautopilot mode annunciators on the G1000 PFD. This provides easyviewing of the autopilot operating mode and status, but remains a sup-plemental display of autopilot operating modes.

The GDL 69A is a remote sensor that receives broadcast weather datafrom a service of XM Satellite Radio and delivers the data to to theG--1000 MFD. Highly reliable, near real--time weather information istransmitted to the aircraft via XM Satellite Radio. XM WX SatelliteWeather service operate in the S--band frequency to provide continu-ous uplink capabilities at any altitude throughout North America. Alsoavailable with the GDL--69A is XM’s digital audio entertainment, whichprovides 130--plus channels of music, news, talk, sports and informa-tion. For detailed operating instructions, see Garmin G--1000 CockpitReference Guide for the Mooney M20M.

The TSO’d KN 63, if installed, is a complete 100 watt, 200--channel re-mote DME system. Distances up to 389 nm (at line--of--sight altitude),groundspeedsup to 999knots and time--to--stationup to 99minutes arecomputed digitally and displayed on theG--1000PFDand controlled bythe G--1000 interface controls. Distance lock--on is virtually instanta

MOONEYM20M




neous (usually within one second) with accurate groundspeed andtime--to--station readouts following in less than a minute. For detailedoperating instructions, see Garmin G--1000 Cockpit Reference Guidefor the Mooney M20M.

The TSO’d Becker ADF 3502--(2) Automatic Direction Finder system, ifinstalled, provides accurate bearing--to--station in the 200 kHz to 1799kHz frequency range, complete with ADF, ANT andBFO tuningmodes,plus audio output for station identification and monitoring AM broad-casts. It is displayed on the G--1000 PFD and controlled by the PFD in-terface controls. For detailed operating instructions, see Garmin

G--1000 Cockpit Reference Guide for the Mooney M20M.

Traffic data detected by the L--3 Communications Goodrich SKY-WATCHt Traffic Advisory System (TAS), if installed, will appear on theMFD and traffic display pages of theG--1000. For detailed operating in-structions regarding the interfaceof theG--1000with theSKYWATCHtrefer to the Pilot’s Guide for the SKYWATCHt and theGarminG--1000Cockpit Reference Guide for the Mooney M20M.

Refer to the GARMIN G1000 Cockpit Reference Guide for the M20RMODEL aircraft, GARMIN P/N 00--00450--01, Rev. A or later FAA ap-proved, for complete descriptions of the G1000 system and operatingprocedures.

7.1 -- LANDING GEAR

Gear down and locked positions are indicated by a single indicator lo-cated on the aircraft floor and a red “GEARWARN” light is located in thesystem indicator lights, as well as a green “GEAR DWN” indicator. Re-fer to the aircraft POH/AFM for additional information.

7.2 -- ELECTRICAL SYSTEM

TheM20M has a 28 Volt DC system, powered by dual 70--amp alterna-tors, which aremounted on the front of the engine. Both are driven by Vbelts on the starter ring gear and both alternators charge the main bat-teries. The alternator are the primary source of aircraft power and isconnected to the aircraft electrical system at the main bus. In the eventof an alternator failure, the remaining alternator has sufficient capabilityto power all aircraft systems.

Additional battery power is stored in two 11 amp--hour, lead acid batter-ies, which are mounted in the tailcone of the aircraft, and either batterymay feed both the essential and non--essential busses. In the event ofboth alternators failing, the EMERBUS switch can be activated and theselected main battery will power the following:

MOONEYM20M




S A reduced subset of the G1000 system, which is comprised of thePFD/MFD, AHRS, ADC, Com1, Nav1, GPS1, Transponder, AudioPanel, and Engine Instruments;

S An independent, standby attitude indicator (artificial horizon)S Lighting for the attitude indicator, altimeter, airspeed indicator, and

compass.S AuxOverheadEquipment,AuxPowerEquipment, and IceProtec-

tion System.

When the EMER BUS switch is set to ON, the Emergency Bus annun-ciator is activated, andnonessential equipment is shed from thebus. .Asingleoperatingalternatorwill provideenoughcurrent to supply all elec-trical equipment needed for safe flight, but if both alternators havefailed, the battery voltage should be monitored, and additional loadshedding may be required Activating the EMER BUS switch bypassesthe Master Switch and electrically feeds the standby attitude indicatorand all standby lighting using both main batteries.

The circuit breaker panel is located on the right side of the instrumentpanel. Each breaker is clearly marked to show which circuit it protects.Also, circuit provisions are made to handle the addition of communica-tions and navigation equipment.

Standard electrical accessories include the starter, the electric fuelpump, and the stall warning horn. Electrical accessories include thenavigation lights, anti--collision strobe lights, instrument panel lighting,and cabin courtesy lights. Make sure the lighting and Emergency Busswitch are off when leaving the aircraft. Leaving the lights on for an ex-tended period of time could cause depletion of the battery.

Two lights, mounted in the overhead panel, provide instrument andcockpit lighting for night flying, in addition glare shield lighting may becontrolled via a dimmer switch on the lower right side of the instrumentpanel.. Wing tip recognition lights and landing/taxi lights are operatedby a rocker type switchesmounted in the overhead switch panel. Land-ing and taxi lights are mounted on the wing leadings edges on bothwings.

The M20M electrical system is divided into two power buses. A simpli-fied schematic of the electrical system is shown in the diagram, whichfollows this electrical system description.

ESSENTIAL BUS

The Essential bus is tied directly to the main aircraft battery via the se-lected battery contactor.When theMaster Switch is turned on, power isimmediately supplied to the Essential and non--Essential busses. TheEssential bus provides power to theG1000 equipment and to the back-

MOONEYM20M




up instruments. When the Emergency Bus switch is activated by thepilot, the non essential bus is shed from the essential bus. The selectedmain battery (two main batteries are available) remains online.

NON - ESSENTIAL BUS

The non--essential bus powers the autopilot, turn coordinator requiredfor the autopilot, the Stormscope, and GIA #2. This bus load is shedwhen the EMER GUS switch is activated.

EQUIPMENT LOCATION

The G1000 ADC and GEA LRU’s are located behind the instrumentpanel. The PFD, MFD, and Audio Panel are mounted to the panel andmay be removed using a hexagonal tool. Themagnetometer is locatedin the rightwing outboard of the landing light. TheAHRS, and remainingLRU’s are located behind the cabin near the main batteries.

Power is stored in two 11 amp--hour lead acid battery which aremounted in the tailcone of the aircraft, and either battery may feed boththe essential and non--essential busses. In the event of an alternatorfailure, the standby alternator and selected main battery will power thefollowing:

MOONEYM20M




M20MPOWERSUMMARY

M20M POWER SUMMARY

MOONEYM20M




7.3 -- VACUUM SYSTEM

GX aircraft are all electric, there is no Vacuum System in the standardaircraft.

7.4 -- INSTRUMENT PANEL

The instrument panel hasbeendesigned to incorporate theG1000 Inte-grated Cockpit. All Communications, Navigation, Engine Instruments,and System annunciations have been integrated into a custom designpackage specifically for the M20M series aircraft.

Engine and electrical switches are located on the left side of the switchpanel. Nav, strobe, recognition / landing and taxi light switches are lo-cated on the overhead switch panel.

Instrument panel lighting is provided by post lights, overhead panellights and the internally lightedG1000 IntegratedCockpit System. Opti-mum cockpit panel lighting for night flying is achieved by using a com-bination of panel lights and overhead map lights.

SECTION VIII – HANDLING AND SERVICING

No change.

SECTION IX – SUPPLEMENTAL DATA

Add this supplement to this Section.

SECTION X – SAFETY TIPS

No change.

garmin g1000 integrated avionics system installed in ... · garmin g1000 integrated avionics system...

Documents